Aircraft taking off and landing system and method

An aircraft and fuselage technology, applied in the field of aircraft, can solve problems such as high power consumption

Inactive Publication Date: 2017-06-09
FOSHAN SHENFENG AVIATION SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Traditional multi-axis UAVs have vertical take-off and landing, and take-off and landing requ...

Method used

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  • Aircraft taking off and landing system and method
  • Aircraft taking off and landing system and method

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Embodiment Construction

[0010] Now in conjunction with accompanying drawing, the present invention is described in detail: comprise fixed-wing aircraft, left four-axis unmanned aerial vehicle 61, right four-axis unmanned aerial vehicle 62 and rear four-axis unmanned aerial vehicle 63; Fixed-wing aircraft comprises fuselage 3, wing, Empennage 2, left joint part 71, right joint part 73 and rear joint part 72; Wing comprises left wing 1 and right wing, and left wing 1 and right wing structure are identical and symmetrical division is in fuselage 3 axis; Left joint part 71 is embedded in Left wing 1 bottom; Right joint 73 is embedded in right wing bottom; Rear joint 72 is embedded in fuselage 3 abdomen and is close to the part of empennage 2; Left joint 71, right joint 73 and rear joint 72 functional structures are identical, The left joint 71, the right joint 73 and the rear joint 72 are used to securely connect the joint head 8 of the left four-axis drone 61, the right four-axis drone 62 and the rear fo...

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Abstract

The invention provides a fixed-wing aircraft taking off and landing system and method, belongs to the technical field of air vehicles, and particularlyrelates to a fixed-wing aircraft taking off and landing system and method. The system comprises a left four axis unmanned aerial vehicle, a right four axis unmanned aerial vehicle, a fixed wing aircraft and a back four axis unmanned aerial vehicle; the fixed wing aircraft is provided witha left combined section, a right combined sectionand a back combined section; each of the three four axis unmanned aerial vehicles comprises a fixed board and a combined rod, the combined rod comprises a combined head; when the aircraft takes off, the combined heads of the three combined rodsare embedded inthe three combined sections of the fixed wing aircraft, the three four axis unmanned aerial vehicles carry the fixed wing aircraft and are separated after the aircraft takes off; when the aircraft lands on the ground, the three four axis unmanned aerial vehicles are launched in the sky and combined with the fixed wing aircraft, the three combined headsare embedded in the three combined sections, and the three four axis unmanned aerial vehicles carry the fixed wing aircraft to land. The fixed-wing aircraft taking off and landing system and method exploitwell the advantages of the vertical taking off and landing of the four axisunmanned aerial vehicles, further overcome the disadvantage that the taking off or landing of the fixedwing aircraft needs the assistance of the runway;furthermore a way of aircraft taking off and landing is invented.

Description

technical field [0001] An aircraft take-off and landing system and method belong to the technical field of aircraft, and in particular relate to the aircraft take-off and landing system and method. Background technique [0002] Traditional fixed-wing aircraft generally need to rely on the landing gear to taxi and land, and take off and land requires a long runway, and a special airport can be used to land. In addition, the weight of the landing gear accounts for about 3-5% of the landing weight of the aircraft. After landing, it becomes a burden on the aircraft, increases the fuel consumption of the aircraft, and is not conducive to the long-term flight of the aircraft. Studies have shown that no landing gear system can save aircraft fuel consumption by 10-20%. Traditional multi-axis UAVs have vertical take-off and landing, and take-off and landing require little space, but due to high power consumption, they are not suitable for long-duration flight. Contents of the inve...

Claims

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Application Information

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IPC IPC(8): B64D5/00B64C29/00
CPCB64C29/00B64D5/00B64U70/20
Inventor 王志成陈亚安罗哲远李玉龙谭俭辉
Owner FOSHAN SHENFENG AVIATION SCI & TECH
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